High and low spool accessory gearbox drive

ABSTRACT

A gas turbine engine comprises a low speed spool and a high speed spool, with each of the spools including a turbine to drive a respective one of the spools. The high speed spool rotates at a higher speed than the low speed spool. A high speed power takeoff is driven to rotate by the high speed spool, and a low speed power takeoff is driven to rotate by the low speed spool. The high speed power takeoff drives a starter generator and a permanent magnet alternator. The low speed power takeoff drives a variable frequency generator.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a continuation of U.S. patent application Ser. No.15/484,376 filed on Apr. 11, 2017.

BACKGROUND OF THE INVENTION

This application relates to an accessory gearbox drive for a gas turbineengine wherein a low spool drives a variable frequency generator alongwith other components.

Gas turbine engines are known and typically include a pair of spools.

A fan delivers air into a bypass duct as propulsion air and alsodelivers air into a core engine. Air passing into the core enginereaches a low pressure compressor and then passes to a high pressurecompressor. The air compressed by the high pressure compressor isdelivered into a combustor where it is mixed with fuel and ignited.Products of this combustion pass downstream over a high pressure turbinerotor.

The high pressure turbine rotor is driven to rotate and rotates the highpressure compressor. A low pressure turbine rotor is downstream of thehigh pressure turbine and is also driven to rotate. The low pressureturbine rotates with the low pressure compressor as a low speed spool.Further, the low pressure turbine may drive the fan rotor through a gearreduction.

A number of accessories, such as generators, starters, pumps, etc., arepowered by accessory gearboxes which are driven to rotate with eitherthe high or low pressure spool. Traditionally, the high pressure spoolhas driven most of these accessories.

However, this reduces the overall efficiency of the engine. Thus, it hasbeen proposed to drive at least some accessories off the low speedspool.

SUMMARY OF THE INVENTION

In a featured embodiment, a gas turbine engine comprises a low speedspool and a high speed spool, with each of the spools including aturbine to drive a respective one of the spools. The high speed spoolrotates at a higher speed than the low speed spool. A high speed powertakeoff is driven to rotate by the high speed spool, and a low speedpower takeoff is driven to rotate by the low speed spool. The high speedpower takeoff drives a starter generator and a permanent magnetalternator. The low speed power takeoff drives a variable frequencygenerator.

In another embodiment according to the previous embodiment, a firsttransmission is driven by the low speed or power takeoff, and the firsttransmission drives the variable frequency generator at a plurality ofspeeds.

In another embodiment according to any of the previous embodiments, thefirst transmission also drives a hydraulic pump at one of a plurality ofdistinct speeds relative to an input speed from the low speed powertakeoff.

In another embodiment according to any of the previous embodiments, acontroller controls the first transmission to achieve a desired inputspeed for the variable frequency generator.

In another embodiment according to any of the previous embodiments, thecontroller also controls the first transmission to drive a hydraulicpump at a desired speed.

In another embodiment according to any of the previous embodiments, thelow speed power takeoff also drives an oil pump.

In another embodiment according to any of the previous embodiments,cooling air is tapped from a location in a compressor section which isupstream of a most downstream location in the compressor section and thetapped air is passed through a heat exchanger and through a cooling aircompressor.

In another embodiment according to any of the previous embodiments, thelow speed spool power takeoff drives the cooling air compressor.

In another embodiment according to any of the previous embodiments, asecond transmission is driven by the low power takeoff to drive thecooling air compressor at a desired speed.

In another embodiment according to any of the previous embodiments, thesecond transmission is a three-speed transmission.

In another embodiment according to any of the previous embodiments, thecontroller controls the second transmission to achieve a desired speedfor the cooling air compressor.

In another embodiment according to any of the previous embodiments,cooling air is tapped from a location in a compressor section which isupstream of a most downstream location in the compressor section and thetapped air is passed through a heat exchanger and through a cooling aircompressor.

In another embodiment according to any of the previous embodiments, thelow speed spool power takeoff drives the cooling air compressor.

In another embodiment according to any of the previous embodiments, asecond transmission is driven by the low power takeoff to drive thecooling air compressor at a desired speed.

In another embodiment according to any of the previous embodiments, thesecond transmission is a three-speed transmission.

In another embodiment according to any of the previous embodiments, thecontroller controls the second transmission to achieve a desired speedfor the cooling air compressor.

In another embodiment according to any of the previous embodiments, thecontroller controls the first transmission to achieve a desired inputspeed tor the variable frequency generator.

In another embodiment according to any of the previous embodiments, thecontroller also controls the first transmission to drive a hydraulicpump at a desired speed.

In another embodiment according to any of the previous embodiments,cooling air is tapped from a location in a compressor section which isupstream of a most downstream location in the compressor section and thetapped air is passed through a heat exchanger and through a cooling aircompressor.

In another embodiment according to any of the previous embodiments, asecond transmission is driven by the low power takeoff to drive thecooling air compressor at a desired speed.

These and other features may be best understood from the followingdrawings and specification.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1A schematically shows a gas turbine engine.

FIG. 1B shows an optional feature for delivering cooling air to aturbine section.

FIG. 2A shows an accessory drive arrangement.

FIG. 2B schematically shows the arrangement of FIG. 2A.

DETAILED DESCRIPTION

FIG. 1A schematically illustrates a gas turbine engine 20. The gasturbine engine 20 is disclosed herein as a two-spool turbofan thatgenerally incorporates a fan section 22, a compressor section 24, acombustor section 26 and a turbine section 28. Alternative engines mightinclude an augmentor section (not shown) among other systems orfeatures. The fan section 22 drives air along a bypass flow path B in abypass duct defined within a nacelle 15, while the compressor section 24drives air along a core flow path C for compression and communicationinto the combustor section 26 then expansion through the turbine section28. Although depicted as a two-spool turbofan gas turbine engine in thedisclosed non-limiting embodiment, it should be understood that theconcepts described herein are not limited to use with two-spoolturbofans as the teachings may be applied to other types of turbineengines including three-spool architectures.

The exemplary engine 20 generally includes a low speed spool 30 and ahigh speed spool 32 mounted for rotation about an engine centrallongitudinal axis A relative to an engine static structure 36 viaseveral bearing systems 38. It should be understood that various bearingsystems 38 at various locations may alternatively or additionally beprovided, and the location of bearing systems 38 may be varied asappropriate to the application.

The low speed spool 30 generally includes an inner shaft 40 thatinterconnects a fan 42, a first (or low) pressure compressor 44 and afirst (or low) pressure turbine 46. The inner shaft 40 is connected tothe fan 42 through a speed change mechanism, which in exemplary gasturbine engine 20 is illustrated as a geared architecture 48 to drivethe fan 42 at a lower speed than the low speed spool 30. The high speedspool 32 includes an outer shaft 50 that interconnects a second (orhigh) pressure compressor 52 and a second (or high) pressure turbine 54.A combustor 56 is arranged in exemplary gas turbine 20 between the highpressure compressor 52 and the high pressure turbine 54. A mid-turbineframe 57 of the engine static structure 36 is arranged generally betweenthe high pressure turbine 54 and the low pressure turbine 46. Themid-turbine frame 57 further supports bearing systems 38 in the turbinesection 28. The inner shaft 40 and the outer shaft 50 are concentric androtate via bearing systems 38 about the engine central longitudinal axisA which is collinear with their longitudinal axes.

The core airflow is compressed by the low pressure compressor 44 thenthe high pressure compressor 52, mixed and burned with fuel in thecombustor 56, then expanded over the high pressure turbine 54 and lowpressure turbine 46. The mid-turbine frame 57 includes airfoils 59 whichare in the core airflow path C. The turbines 46, 54 rotationally drivethe respective low speed spool 30 and high speed spool 32 in response tothe expansion. It will be appreciated that each of the positions of thefan section 22, compressor section 24, combustor section 26, turbinesection 28, and fan drive gear system 48 may be varied. For example,gear system 48 may be located aft of combustor section 26 or even aft ofturbine section 28, and fan section 22 may be positioned forward or aftof the location of gear system 48.

The engine 20 in one example is a high-bypass geared aircraft engine. Ina further example, the engine 20 bypass ratio is greater than about six(6), with an example embodiment being greater than about ten (10), thegeared architecture 48 is an epicyclic gear train, such as a planetarygear system or other gear system, with a gear reduction ratio of greaterthan about 2.3 and the low pressure turbine 46 has a pressure ratio thatis greater than about five. In one disclosed embodiment, the engine 20bypass ratio is greater than about ten (10:1), the fan diameter issignificantly larger than that of the low pressure compressor 44, andthe low pressure turbine 46 has a pressure ratio that is greater thanabout five 5:1. Low pressure turbine 46 pressure ratio is pressuremeasured prior to inlet of low pressure turbine 46 as related to thepressure at the outlet of the low pressure turbine 46 prior to anexhaust nozzle. The geared architecture 48 may be an epicycle geartrain, such as a planetary gear system or other gear system, with a gearreduction ratio of greater than about 2.3:1. It should be understood,however, that the above parameters are only exemplary of one embodimentof a geared architecture engine and that the present invention isapplicable to other gas turbine engines including direct driveturbofans.

A significant amount of thrust is provided by the bypass flow B due tothe high bypass ratio. The fan section 22 of the engine 20 is designedfor a particular flight condition—typically cruise at about 0.8 Mach andabout 35,000 feet (10,668 meters). The flight condition of 0.8 Mach and35,000 ft (10,668 meters), with the engine at its best fuelconsumption—also known as “bucket cruise Thrust Specific FuelConsumption (‘TSFC’)”—is the industry standard parameter of lbm of fuelbeing burned divided by lbf of thrust the engine produces at thatminimum point. “Low fan pressure ratio” is the pressure ratio across thefan blade alone, without a Fan Exit Guide Vane (“FEGV”) system. The lowfan pressure ratio as disclosed herein according to one non-limitingembodiment is less than about 1.45. “Low corrected fan tip speed” is theactual fan tip speed in ft/sec divided by an industry standardtemperature correction of [(Tram ° R)/(518.7° R)]^(0.5). The “Lowcorrected fan tip speed” as disclosed herein according to onenon-limiting embodiment is less than about 1150 ft/second (350.5meters/second).

FIG. 1A also shows a power takeoff or power shaft 80 being driven torotate with the high speed spool 32 and driving accessory gears 82. Atthe same time, a second power takeoff or power shaft 84 rotates with thelow speed spool 30 and drives additional accessories shown schematicallyat 86.

FIG. 1B shows an optional feature. A tap 87 taps cooling air from alocation in the compressor section 24 which is upstream of a downstreammost point in the compressor section. Tapping the air from this moreupstream location increases the efficiency of the engine compared totapping the highly compressed air downstream of the last stage of thehigh pressure compressor 52. However, this tapped air is not at asufficiently high pressure to necessarily enter the turbine section 28for cooling. Thus, a cooling air compressor 88 is provided to increasethe pressure of the air from tap 87. Downstream of the compressor 88,the air passes through a heat exchanger 90 where it is cooled by airsuch as the bypass air B. Downstream of the heat exchanger 90, the airpasses into a line 91 and moves to cool components in the turbinesection 28. Such systems have been generally proposed.

FIG. 2A shows an arrangement for driving a number of accessories. Asshown in FIG. 2A, the shaft 80 drives a bevel gear 100 which drives asecond bevel gear 101 which rotates to drive accessories, as will beexplained below.

The shaft 84 drives a gear 102 to drive a gear 103 which is associatedwith the shaft for driving accessories driven by the low speed shaft 84.

As shown, the shaft driven by gear 101 includes a starter generator 104and a permanent magnet alternator 106. These components are necessaryfor initially starting the gas turbine engine. The permanent magnetalternator is necessary to start or “fire up” a controller 107 for theengine, which is shown schematically. The starter generator 104 beginsrotation of the engine at start-up, as is known.

By minimizing the number of components driven by the high speed drivenshaft 80, the efficiency of the overall engine is increased.

The gear 103 drives a shaft 109 drive a gearbox 110, which drives anumber of components through a plurality of gears 112, 114, 116, 118.The gears allow the various accessories to be driven by the shaft 84 torotate at different speeds.

As shown, the cooling air compressor 88 may be driven by the shaft 84.In the disclosed embodiment, the gear 112 drives a transmission 108,which actually drives the compressor 88 at a desired speed. The use ofthe transmission 108 allows the speed of the compressor 88 to be keptcloser to a constant value than it might otherwise see from the input atshaft 84. That is, it is known that the input from the high speed spool80 will be closer to constant than would be the input speed to the shaft84. The use of the transmission, which may be a three-speed transmission108, allows the ultimate speed of the compressor 88 to be kept closer toa desired constant value.

In addition, a variable frequency generator 120 is driven by atransmission 122, which may also be a three-speed transmission. Hereagain, the transmission 122 keeps the speed of the variable frequencygenerator 120 closer to constant such that the output of the generatorwill be more readily useable.

In addition, a hydraulic pump 124 is provided for supplying hydraulicfluid across the engine. Hydraulic pump 124 may also be driven by thethree-speed transmission 122.

In addition, an oil pump 126 is driven by the input shaft 109 and may bedriven through the several gears in the gearbox 110 to achieve a desiredspeed.

FIG. 2B schematically shows the drive inputs into the severalcomponents. As shown, the shaft 80 drives the starter generator 104 andpermanent magnet alternator 106 on a common shaft.

The drive shaft 109 is driven by shaft 84, and drives a plurality ofgears in a gearbox 110 to drive a three-speed transmission 122 to drivea variable frequency generator 120.

Similarly, the gearbox 110 drives a three-speed transmission 108 toultimately drive the cooling air compressor 88.

The controller 107 may also control the three-speed transmissions 108and 122 to achieve desired speeds for the cooling compressor 88,variable frequency generator 120 and pump 124. A worker of ordinaryskill in the art would recognize how to control the transmissions 108and 122 to achieve this goal. Also, as mentioned, the transmission 122controls the speed of the hydraulic pump 124. Further, the shaft 109also drives the pump 126.

Although an embodiment of this invention has been disclosed, a worker ofordinary skill in this art would recognize that certain modificationswould come within the scope of this invention. For that reason, thefollowing claims should be studied to determine the true scope andcontent of this invention.

The invention claimed is:
 1. A gas turbine engine comprising: a lowspeed spool and a high speed spool, with each of said spools including aturbine to drive a respective one of said spools; said high speed spoolrotating at a higher speed than said low speed spool; a high speed powertakeoff driven to rotate by said high speed spool, and a low speed powertakeoff driven to rotate by said low speed spool; said high speed powertakeoff driving a starter generator and a permanent magnet alternator;said low speed power takeoff driving a variable frequency generator;wherein a first transmission is driven by said low speed power takeoff,and said first transmission driving said variable frequency generator ata plurality of speeds; and wherein a controller controls said firsttransmission to achieve a desired input speed for said variablefrequency generator.
 2. The gas turbine engine as set forth in claim 1,wherein said first transmission also driving a hydraulic pump at one ofa plurality of distinct speeds relative to an input speed from said lowspeed power takeoff.
 3. The gas turbine engine as set forth in claim 2,wherein said controller also controls said first transmission to drive ahydraulic pump at a desired speed.
 4. The gas turbine engine as setforth in claim 3, wherein said low speed power takeoff also driving anoil pump.
 5. The gas turbine engine as set forth in claim 1, whereinsaid low speed spool driving a fan rotor through a gear reduction. 6.The gas turbine engine as set forth in claim 5, wherein said firsttransmission also driving a hydraulic pump at one of a plurality ofdistinct speeds relative to an input speed from said low speed powertakeoff.
 7. The gas turbine engine as set forth in claim 6, wherein saidcontroller also controls said first transmission to drive a hydraulicpump at a desired speed.
 8. The gas turbine engine as set forth in claim7, wherein said low speed power takeoff also driving an oil pump.
 9. Thegas turbine engine as set forth in claim 8, wherein a gear ratio of saidgear reduction is greater than 2.3.
 10. The gas turbine engine as setforth in claim 5, wherein said controller also controls said firsttransmission to drive a hydraulic pump at a desired speed.
 11. The gasturbine engine as set forth in claim 5, wherein a gear ratio of saidgear reduction is greater than 2.3.
 12. The gas turbine engine as setforth in claim 5, wherein said low speed power takeoff also driving anoil pump.
 13. The gas turbine engine as set forth in claim 1, whereinsaid low speed power takeoff also driving an oil pump.
 14. The gasturbine engine as set forth in claim 1, wherein said control is providedwith power at start up by said permanent magnet alternator.